.............................................

Atlas-V Rocket

Description:

The Lockheed Martin Atlas V resulted from
Lockheed Martin's combination of the best practices from both the Atlas
and Titan programs into an evolved commercial and government launch
system for the 21st century. Atlas V builds on the design innovations
demonstrated on Atlas III and incorporates a structurally stable
booster propellant tank, enhanced payload fairing options and optional
strap-on solid rocket boosters.

All nine Atlas V to date were
successfully launched. The Atlas V family uses a single-stage Atlas
main engine, the Russian RD-180 and the newly developed Common Core
Booster (CCB)TM with up to five strap-on solid rocket boosters. The
CCBTM is 12.5 ft. (3.8 m) in diameter by 106.6 ft. (32.5m) long and
uses 627,105 lbs. (284,453 kg) of liquid oxygen and RP-1 rocket fuel
propellants.

Additionally, on Atlas V, Lockheed Martin
introduced a 4.57-meter usable diameter Contraves payload fairing in
addition to retaining the option to use the heritage Atlas payload
fairings. The Contraves fairing is a composite design and is based on
flight proven hardware. Three configurations will be manufactured to
support Atlas V. The short and medium length configurations will be
used on the Atlas V 500 series.

The Centaur upper stage uses a
pressure stabilized propellant tank design and cryogenic propellants.
The Centaur stage for Atlas V is stretched 5.5 ft (1.68 m) and is
powered by either one or two Pratt & Whitney RL10A-4-2 engines,
each engine developing a thrust of 22,300 lbs. (99.2 kN). Operational
and reliability upgrades are enabled with the RL10A-4-2 engine
configuration. The inertial navigation unit (INU) located on the
Centaur provides guidance and navigation for both Atlas and Centaur,
and controls both Atlas and Centaur tank pressures and propellant use.
The Centaur engines are capable of multiple in-space starts, making
possible insertion into low-earth parking orbit, followed by a coast
period and then insertion into GTO.